Hydrostatic non-contact seal with weight reduction pocket

ABSTRACT

A non-contact seal assembly is provided. The non-contact seal assembly includes a plurality of seal shoes arranged about a centerline in an annular array, the seal shoes include a first seal shoe extending axially along the centerline between a first shoe end and a second shoe end. The non-contact seal assembly may comprise a seal base circumscribing the annular array of the seal shoes. The non-contact seal assembly may further comprise a plurality of spring elements, each of the spring elements radially between and connecting a respective one of the seal shoes with the seal base, where the plurality of seal shoes each includes a weight reduction pocket formed in a circumferential region of the seal shoe.

This invention was made with government support under Contract No.FA8650-09-D-2923-0021 awarded by the United States Air Force. Thegovernment may have certain rights in the invention.

BACKGROUND 1. Technical Field

The present disclosure relates generally to hydrostatic non-contactseals. More particularly, the disclosure relates to hydrostaticnon-contact seals with a weight reduction pocket.

2. Background Information

Rotational equipment typically includes one or more seal assemblies forsealing gaps between rotors and stators. A typical seal assemblyincludes a contact seal with a seal element such as a knife edge sealthat engages a seal land. Such a contact seal, however, can generate asignificant quantity of heat which can reduce efficiency of therotational equipment as well as subject other components of therotational equipment to high temperatures and internal stresses. Toaccommodate the high temperatures and stresses, certain components ofthe rotational equipment may be constructed from specialty hightemperature materials, which can significantly increase themanufacturing and servicing costs as well as the mass of the rotationalequipment.

It would be desirable to reduce the mass of the seal to reduce overallengine weight, and to better optimize the vibrational response of theseal system.

SUMMARY OF THE DISCLOSURE

The following presents a simplified summary in order to provide a basicunderstanding of some aspects of the disclosure. The summary is not anextensive overview of the disclosure. It is neither intended to identifykey or critical elements of the disclosure nor to delineate the scope ofthe disclosure. The following summary merely presents some concepts ofthe disclosure in a simplified form as a prelude to the descriptionbelow.

Aspects of the disclosure are directed to a non-contact seal assembly,having a plurality of seal shoes arranged about a centerline in anannular array, the seal shoes include a first seal shoe extendingaxially along the centerline between a first shoe end and a second shoeend. The non-contact seal assembly may comprise a seal basecircumscribing the annular array of the seal shoes. The non-contact sealassembly may further comprise a plurality of spring elements, each ofthe spring elements radially between and connecting a respective one ofthe seal shoes with the seal base, where the plurality of seal shoeseach includes a weight reduction pocket formed in a circumferentialregion of the seal shoe.

Each of the plurality of first and second seal shoes includes opposingfirst and second circumferential sides, and the first circumferentialside includes a first weight reduction pocket.

Each of the plurality of first and second seal shoes includes opposingfirst and second circumferential sides, and the first circumferentialside includes a first weight reduction pocket and the secondcircumferential side includes a second weight reduction pocket.

The first weight reduction pocket forms a through hole in the firstcircumferential side.

The first weight reduction pocket forms a first through hole in thefirst circumferential side and the second weight reduction pocket formsa second through hole in the second circumferential side.

The plurality of seal shoes, the seal base and the plurality of springelements are formed from nickel alloy.

The plurality of seal shoes, the seal base and the plurality of springelements are formed from cobalt alloy.

The first seal shoe extends circumferentially, at the first shoe end,between a first shoe side and a second shoe side for a seal shoe length.

The seal shoes collectively form a substantially annular end surface atthe second shoe end.

According to another aspect of the present disclosure, a non-contactseal assembly is provided. The non-contact seal assembly may provide aplurality of seal shoes arranged about a centerline in an annular array,the seal shoes including a first seal shoe extending axially along thecenterline between a first shoe end and a second shoe end. Thenon-contact seal assembly may comprise a seal base circumscribing theannular array of the seal shoes. The non-contact seal assembly mayfurther comprise a plurality of spring elements, each of the springelements radially between and connecting a respective one of the sealshoes with the seal base, where the plurality of seal shoes eachincludes a weight reduction pocket formed in a circumferential region ofa seal shoe stop that limits radial travel of the seal shoe.

Each of the plurality of first and second seal shoes includes opposingfirst and second circumferential sides each uniquely associated with anassociated one of a first or second shoe stop, and the firstcircumferential side includes a first weight reduction pocket.

Each of the plurality of first and second seal shoes includes opposingfirst and second circumferential sides, where the first circumferentialside includes a first weight reduction pocket and the secondcircumferential side includes a second weight reduction pocket.

The first weight reduction pocket forms a through hole in the firstcircumferential side.

The first weight reduction pocket forms a first through hole in thefirst circumferential side and the second weight reduction pocket formsa second through hole in the second circumferential side.

The plurality of seal shoes, the seal base and the plurality of springelements are formed from nickel alloy.

The plurality of seal shoes, the seal base and the plurality of springelements are formed from cobalt alloy.

The first seal shoe extends circumferentially, at the first shoe end,between a first shoe side and a second shoe side for a seal shoe length.

The seal shoes collectively form a substantially annular end surface atthe second shoe end.

According to another aspect of the present disclosure, an assembly forrotational equipment with an axial centerline is provided. The assemblymay comprise a stator structure and a rotor structure. The assembly maycomprise a seal assembly configured to substantially seal an annular gapbetween the stator structure and the rotor structure, the seal assemblycomprising a hydrostatic non-contact seal device including a pluralityof seal shoes, a seal base and a plurality of spring elements. The sealshoes arranged about a centerline in an annular array, the seal shoessealingly engaging the rotor structure and including a first seal shoeextending axially along the centerline between a first shoe end and asecond shoe end. The seal base circumscribing the annular array of theseal shoes, the seal base mounted with the stator structure, where theplurality of seal shoes each includes a weight reduction pocket formedin a circumferential region of the seal shoe.

Each of the plurality of first and second seal shoes includes opposingfirst and second circumferential sides, and the first circumferentialside includes a first weight reduction pocket and the secondcircumferential side includes a second weight reduction pocket.

BRIEF DESCRIPTION OF THE DRAWINGS

The present disclosure is illustrated by way of example and not limitedin the accompanying figures in which like reference numerals indicatesimilar elements. The drawing figures are not necessarily drawn to scaleunless specifically indicated otherwise.

FIG. 1 is a top half side sectional illustration of an assembly forrotational equipment.

FIG. 2 is a simplified isometric illustration of a primary seal devicefor the assembly of FIG. 1.

FIG. 3 is an illustration of a hydrostatic non-contact seal with a firstweight reduction pocket located at a first circumferential side of theseal shoe of the seal.

FIG. 4 is an illustration of hydrostatic non-contact seal with a secondweight reduction pocket located at a second circumferential side of theseal shoe.

FIG. 5 is a side cutaway illustration of a gas turbine engine.

DETAILED DESCRIPTION

It is noted that various connections are set forth between elements inthe following description and in the drawings (the contents of which areincorporated in this specification by way of reference). It is notedthat these connections are general and, unless specified otherwise, maybe direct or indirect and that this specification is not intended to belimiting in this respect. A coupling between two or more entities mayrefer to a direct connection or an indirect connection. An indirectconnection may incorporate one or more intervening entities or aspace/gap between the entities that are being coupled to one another.

Aspects of the disclosure may be applied in connection with a gasturbine engine.

FIG. 1 illustrates an assembly 20 for rotational equipment with an axialcenterline 22. An example of such rotational equipment is a gas turbineengine for an aircraft propulsion system, an exemplary embodiment ofwhich is described below in further detail. However, the assembly 20 ofthe present disclosure is not limited to such an aircraft or gas turbineengine application. The assembly 20, for example, may alternatively beconfigured with rotational equipment such as an industrial gas turbineengine, a wind turbine, a water turbine, or any other apparatus in whicha seal is provided between a stator structure and a rotor structure.

The assembly 20 of FIG. 1 includes a stator structure 24, a rotorstructure 26 and a seal assembly 28. This seal assembly 28 is mountedwith the stator structure 24, and configured to substantially seal anannular gap 30 between the stator structure 24 and the rotor structure26 as described below in further detail.

The stator structure 24 includes a seal carrier 32. This seal carrier 32may be a discrete, unitary annular body. Alternatively, the seal carrier32 may be configured with another component/portion of the statorstructure 24. The seal carrier 32 has an inner radial seal carriersurface 34. This seal carrier surface 34 may be substantiallycylindrical, and extends circumferentially around and faces towards theaxial centerline 22. The seal carrier surface 34 at least partiallyforms a bore in the stator structure 24. This bore is sized to receivethe seal assembly 28, which may be fixedly attached to the seal carrier32 by, for example, a press fit connection between the seal assembly 28and the seal carrier surface 34.

The rotor structure 26 includes a seal land 36. This seal land 36 may bea discrete, unitary annular body. Alternatively, the seal land 36 may beconfigured with another component/portion of the rotor structure 26. Theseal land 36 has an outer radial seal land surface 38. This seal landsurface 38 may be substantially cylindrical, and extendscircumferentially around and faces away from the axial centerline 22.The seal land surface 38 is disposed to face towards and is axiallyaligned with the seal carrier surface 34. While FIG. 1 illustrates thesurfaces 34 and 38 with approximately equal axial lengths along theaxial centerline 22, the seal land surface 38 may alternatively belonger or shorter than the seal carrier surface 34 in other embodiments.

The seal assembly 28 includes a primary seal device 40 and one or moresecondary seal devices 42; e.g., 1, 2, 3 or more secondary seal devices42. The seal assembly 28 also includes one or more additional componentsfor positioning, supporting and/or mounting one or more of the sealdevices 40 and 42 with the stator structure 24. The seal assembly 28 ofFIG. 1, for example, includes a first ring structure 44 configured forpositioning, supporting and/or mounting the secondary seal devices 42relative to the primary seal device 40. This first ring structure 44 mayalso be configured for axially positioning and/or supporting a secondend surface 46 of the primary seal device 40 relative to the statorstructure 24. The seal assembly 28 of FIG. 1 also includes a second ringstructure 48 (e.g., a scalloped support ring) configured for axiallypositioning and/or supporting a first end surface 50 of the primary sealdevice 40 relative to the stator structure 24. However, the second ringstructure 48 may be omitted where, for example, the first end surface 50of the primary seal device 40 may be abutted against anothercomponent/portion of the stator structure 24 (e.g., an annular orcastellated shoulder) or otherwise axially positioned/secure with thestator structure 24.

The primary seal device 40 may be configured as an annular non-contactseal device and, more particularly, a hydrostatic non-contact sealdevice. An example of such a hydrostatic non-contact seal device is a“HALO™” seal; however, the primary seal device 40 of the presentdisclosure is not limited to the foregoing exemplary hydrostaticnon-contact seal device.

The primary seal device 40 includes a seal base 52, a plurality of sealshoes 54 and a plurality of spring elements 56. The seal base 52 isconfigured as an annular full hoop body, which extends circumferentiallyaround the axial centerline 22. The seal base 52 is configured tocircumscribe the seal shoes 54 as well as the spring elements 56. Theseal base 52 extends axially along the axial centerline 22 between andforms the second end surface 46 and the first end surface 50. The sealbase 52 extends radially between an inner radial base side 58 and anouter radial base side 60, which radially engages (e.g., is press fitagainst) the stator structure 24 and, more particularly, the sealcarrier surface 34 (see FIG. 1).

Referring to FIG. 2, the seal shoes 54 are configured as arcuate bodiesarranged circumferentially about the axial centerline 22 in an annulararray. This annular array of the seal shoes 54 extends circumferentiallyaround the axial centerline 22, thereby forming an inner bore at aninner radial side 62 of the primary seal device 40. As best seen in FIG.1, the inner bore is sized to receive the seal land 36, where the rotorstructure 26 projects axially through (or into) the inner bore formed bythe seal shoes 54.

Referring to FIGS. 1, 3 and 4, each of the seal shoes 54 extendsradially from the inner radial side 62 of the primary seal device 40 toan outer radial surface 64 of that seal shoe 54. Each of the seal shoes54 extends circumferentially around the axial centerline 22 betweenopposing first and second circumferential sides 66 and 68 of that sealshoe 54.

Referring to FIG. 1, each of the seal shoes 54 extends axially along theaxial centerline 22 between a first shoe end 70 and a second shoe end72. The first shoe end 70 may be axially offset from and project axiallyaway from the first end surface 50. The second shoe end 72 may beaxially offset from and project axially away from the second end surface46. The seal shoes 54 of the present disclosure, however, are notlimited to such exemplary relationships.

Each of the seal shoes 54 may include an arcuate end surface 74generally at (e.g., on, adjacent or proximate) the second shoe end 72.In the array (see FIG. 2), these arcuate end surfaces 74 collectivelyform a generally annular (but circumferentially segmented) end surface76 configured for sealingly engaging with the secondary seal devices 42;see FIG. 1. The seal shoes 54 of the present disclosure, however, arenot limited to the foregoing exemplary configuration.

Referring to FIGS. 1, 3 and 4, each of the seal shoes 54 includes one ormore arcuate protrusions 78, which collectively form one or more (e.g.,a plurality of axially spaced) generally annular (e.g.,circumferentially segmented) ribs 80 at the inner radial side 62. Distalinner radial ends 82 of one or more of these ribs 80 are configured tobe arranged in close proximity with (but not touch) and therebysealingly engage the seal land surface 38 in a non-contact manner (seeFIG. 1), where the rotor structure 26 project axially through (or into)the inner bore formed by the seal shoes 54. The ribs 80 therefore areconfigured, generally speaking, as non-contact knife edge seal elements.

Referring to FIG. 2, the spring elements 56 are arrangedcircumferentially about the axial centerline 22 in an annular array.Referring again to FIGS. 3 and 4, the spring elements 56 are alsoarranged radially between the seal shoes 54 and the seal base 52. Eachof the spring elements 56 is configured to connect a respective one ofthe seal shoes 54 with the seal base 52. The spring element 56 shown inFIGS. 3 and 4, for example, includes one or more mounts 83 and 84 (e.g.,generally radial fingers/projections) and one or more beams 86 (e.g.,cantilever-leaf springs). The first mount 83 is connected to arespective one of the seal shoes 54 at (e.g., on, adjacent or proximate)the first circumferential side 66, where the opposing secondcircumferential side 68 of that seal shoe 54 is free floating. Thesecond mount 84 is connected to the seal base 52, and is generallycircumferentially aligned with or near the second circumferential side68. The beams are radially stacked and spaced apart with one another.Each of these beams 86 extends laterally (e.g., tangentially orcircumferentially) from the first mount 83 to the second mount 84. Thesespring elements 56 may thereby laterally overlap a major circumferentialportion (e.g., ˜65-95%) of the seal shoe 54. The spring elements 56 ofthe present disclosure, however, are not limited to the foregoingexemplary configuration or values.

During operation of the primary seal device 40, rotation of the rotorstructure 26 may develop aerodynamic forces and apply a fluid pressureto the seal shoes 54 causing the each seal shoe 54 to respectively moveradially relative to the seal land surface 38. The fluid velocity mayincrease as a gap between the seal shoe 54 and seal land surface 38increases, thus reducing pressure in the gap and drawing the seal shoe54 radially inwardly toward the seal land surface 38. As the gap closes,the velocity may decrease and the pressure may increase within the gap,thus, forcing the seal shoe 54 radially outwardly from the seal landsurface 38. The respective spring element 56 may deflect and move withthe seal shoe 54 to create a primary seal of the gap between the sealland surface 38 and ribs 80 within predetermined design tolerances.

As described above, the radial in and out movement of the seal shoes 54is influenced by the rotational velocity of the rotor structure 26.Where the rotational velocity (w) of the rotor structure 26 has afrequency (f=w÷2π) that is substantially equal to a natural frequency ofthe seal shoes 54, the seal shoes 54 may be subject to natural frequencyexcitation. Such excitation may result in one or more of the following:

-   -   one or more of the seal shoes 54 and, more particularly, one or        more of the ribs 80 to radially contact the seal land surface 38        thereby wearing to one or more of those components 36 and 54;    -   relatively high stresses within one or more of the seal beams        86, which may result in high cycle fatigue failure of one or        more of those seal beams 86; and    -   increased leakage between one or more of the seal shoes 54 and        the seal land surface 38 as a result of an uneven gap between        those components 36 and 54.

The natural frequency of a seal shoe 54 is influenced by the mass of theseal shoe 54 and the stiffness of the spring elements 56 that attach theseal shoe 54 to the seal base 52. Increasing the stiffness of the springelements 56, for example, may increase the natural frequency of thatseal shoe 54. Increasing the stiffness of the spring elements 56 mayadversely affect their stress levels. In another example, decreasing themass of the seal shoe 54 may increase the natural frequency of that sealshoe 54, without adversely impacting stress levels in the springelements 56.

To further increase the natural frequency of the seal, the seal shoe 54may include one or more weight reduction pockets. FIG. 3 is anillustration of a hydrostatic non-contact seal with a first weightreduction pocket 81 located at a first circumferential side 66 of theseal shoe 54. FIG. 4 is an illustration of hydrostatic non-contact sealwith a second weight reduction pocket 85 located at a secondcircumferential side 68 of the seal shoe 54. The weight reductionpockets 81, 85 reduce the weight of the shoe 54, increasing the naturalfrequency of the shoe and its modal response without adversely impactingthe stress levels in the spring elements 56. The size and shape of theweight reduction pockets 81, 85 are selected based upon the desiredmodal response, while ensuring the shoe has the necessary structuralstrength. The shoe may include the first weight reduction pocket, thesecond weight reduction pocket, or both the first and second weightreduction pockets. The weight reduction pockets are not limited to oneor two; it is contemplated that the seal shoe 54 may include a plurality(i.e., two or more) weight reduction pockets. The weight reductionpockets may be formed by machining away material from the shoe to formthe pocket.

Referring again to FIG. 1, while the primary seal device 40 is operableto generally seal the annular gap 30 between the stator structure 24 andthe rotor structure 26 as described above, fluid (e.g., gas) may stillflow axially through passages 96 defined by radial gaps between thecomponents 52, 54 and 56. The secondary seal devices 42 therefore areprovided to seal off these passages 96 and, thereby, further and morecompletely seal the annular gap 30.

Each of the secondary seal devices 42 may be configured as a ring sealelement such as, but not limited to, a split ring. Alternatively, one ormore of the secondary seal devices 42 may be configured as a full hoopbody ring, an annular brush seal or any other suitable ring-type seal.

The secondary seal devices 42 of FIG. 1 are arranged together in anaxial stack. In this stack, each of the secondary seal devices 42axially engages (e.g., contacts) another adjacent one of the secondaryseal devices 42. The stack of the secondary seal devices 42 is arrangedwith the first ring structure 44, which positions and mounts thesecondary seal devices 42 with the stator structure 24 adjacent theprimary seal device 40. In this arrangement, the stack of the secondaryseal devices 42 is operable to axially engage and form a seal betweenthe end surface 76 of the array of the seal shoes 54 and an annularsurface 98 of the first ring structure 44. These surfaces 76 and 98 areaxially aligned with one another, which enables the stack of thesecondary seal devices 42 to slide radially against, but maintainsealingly engagement with, the end surface 76 as the seal shoes 54 moveradially relative to the seal land surface 38 as described above.

The first ring structure 44 may include a secondary seal device supportring 100 and a retention ring 102. The support ring 100 is configuredwith an annular full hoop body, which extends circumferentially aroundthe axially centerline 22. The support ring 100 includes the annularsurface 98, and is disposed axially adjacent and engaged with the sealbase 52.

The retention ring 102 is configured with an annular full hoop body,which extends circumferentially around the axially centerline 22. Theretention ring 102 is disposed axially adjacent and engaged with thesupport ring 100, thereby capturing the stack of the secondary sealdevices 42 within an annular channel formed between the rings 100 and102. The stack of the secondary seal devices 42, of course, may also oralternatively be attached to one of the rings 100 and 102 by, forexample, a press fit connection and/or otherwise.

As described above, the assembly 20 of the present disclosure may beconfigured with various different types and configurations of rotationalequipment. FIG. 5 illustrates one such type and configuration of therotational equipment—a geared turbofan gas turbine engine 106. Such aturbine engine 106 includes various stator structures (e.g., bearingsupports, hubs, cases, etc.) as well as various rotor structures (e.g.,rotor disks, shafts, etc.) as described below, where the statorstructure 24 and the rotor structure 26 can respectively be configuredas anyone of the foregoing structures in the turbine engine 106 of FIG.5, or other structures not mentioned herein.

Referring still to FIG. 5, the turbine engine 106 extends along an axialcenterline 108 (e.g., the centerline 22) between an upstream airflowinlet 110 and a downstream airflow exhaust 112. The turbine engine 106includes a fan section 114, a compressor section 115, a combustorsection 116 and a turbine section 117. The compressor section 115includes a low pressure compressor (LPC) section 115A and a highpressure compressor (HPC) section 115B. The turbine section 117 includesa high pressure turbine (HPT) section 117A and a low pressure turbine(LPT) section 117B.

The engine sections 114-117 are arranged sequentially along thecenterline 108 within an engine housing 118, a portion or component ofwhich may include or be connected to the stator structure 24. Thishousing 118 includes an inner case 120 (e.g., a core case) and an outercase 122 (e.g., a fan case). The inner case 120 may house one or more ofthe engine sections; e.g., an engine core. The outer case 122 may houseat least the fan section 114.

Each of the engine sections 114, 115A, 115B, 117A and 117B includes arespective rotor 124-128. Each of these rotors 124-128 includes aplurality of rotor blades arranged circumferentially around andconnected to one or more respective rotor disks. The rotor blades, forexample, may be formed integral with or mechanically fastened, welded,brazed, adhered and/or otherwise attached to the respective rotordisk(s).

The fan rotor 124 is connected to a gear train 130, for example, througha fan shaft 132. The gear train 130 and the LPC rotor 125 are connectedto and driven by the LPT rotor 128 through a low speed shaft 133. TheHPC rotor 126 is connected to and driven by the HPT rotor 127 through ahigh speed shaft 134. The shafts 132-134 are rotatably supported by aplurality of bearings 136; e.g., rolling element and/or thrust bearings.Each of these bearings 136 is connected to the engine housing 118 by atleast one stationary structure such as, for example, an annular supportstrut.

During operation, air enters the turbine engine 106 through the airflowinlet 110. This air is directed through the fan section 114 and into acore gas path 138 and a bypass gas path 140. The core gas path 138 flowssequentially through the engine sections 115-117. The bypass gas path140 flows away from the fan section 114 through a bypass duct, whichcircumscribes and bypasses the engine core. The air within the core gaspath 138 may be referred to as “core air”. The air within the bypass gaspath 140 may be referred to as “bypass air”.

The core air is compressed by the compressor rotors 125 and 126 anddirected into a combustion chamber 142 of a combustor in the combustorsection 116. Fuel is injected into the combustion chamber 142 and mixedwith the compressed core air to provide a fuel-air mixture. This fuelair mixture is ignited and combustion products thereof flow through andsequentially cause the turbine rotors 127 and 128 to rotate. Therotation of the turbine rotors 127 and 128 respectively drive rotationof the compressor rotors 126 and 125 and, thus, compression of the airreceived from a core airflow inlet. The rotation of the turbine rotor128 also drives rotation of the fan rotor 124, which propels bypass airthrough and out of the bypass gas path 140. The propulsion of the bypassair may account for a majority of thrust generated by the turbine engine106, e.g., more than seventy-five percent (75%) of engine thrust. Theturbine engine 106 of the present disclosure, however, is not limited tothe foregoing exemplary thrust ratio.

The assembly 20 may be included in various aircraft and industrialturbine engines other than the one described above as well as in othertypes of rotational equipment; e.g., wind turbines, water turbines,rotary engines, etc. The assembly 20, for example, may be included in ageared turbine engine where a gear train connects one or more shafts toone or more rotors in a fan section, a compressor section and/or anyother engine section. Alternatively, the assembly 20 may be included ina turbine engine configured without a gear train. The assembly 20 may beincluded in a geared or non-geared turbine engine configured with asingle spool, with two spools (e.g., see FIG. 5), or with more than twospools. The turbine engine may be configured as a turbofan engine, aturbojet engine, a propfan engine, a pusher fan engine or any other typeof turbine engine. The embodiments of the present invention thereforeare not limited to any particular types or configurations of turbineengines or rotational equipment.

While the assembly of the present disclosure has been disclosedprimarily providing a pocket(s) in one or both circumferential ends ofthe seal shoe to reduce weight of the shoe, it is contemplated that theweight reduction can be achieved a number of different ways. Forexample, rather than forming a pocket (i.e., a through or non-throughhole), one of both of the circumferential ends of the shoe may includean area of perforations to reduce weight. In addition, although thepresent disclosure has discussed the seal as being machined to achievethe desired structure, it is contemplated that the seal may also beformed by additive manufacturing.

While various embodiments have been disclosed, it will be apparent tothose of ordinary skill in the art that many more embodiments andimplementations are possible within the scope of the invention. Forexample, the embodiments of the present invention as described hereininclude several aspects and embodiments that include particularfeatures. Although these features may be described individually, it iswithin the scope of the present invention that some or all of thesefeatures may be combined with any one of the aspects and remain withinthe scope of the invention. Accordingly, the present invention is not tobe restricted except in light of the attached claims and theirequivalents.

What is claimed is:
 1. A non-contact seal assembly, comprising: aplurality of seal shoes arranged about a centerline in an annular array,the seal shoes including a first seal shoe extending axially along thecenterline between a first shoe end and a second shoe end; a seal basecircumscribing the annular array of the seal shoes; and a plurality ofspring elements, each of the spring elements radially between andconnecting a respective one of the seal shoes with the seal base, wherethe plurality of seal shoes each includes a weight reduction pocketformed in a circumferential region of the seal shoe.
 2. The non-contactseal assembly of claim 1, where each of the plurality of first andsecond seal shoes includes opposing first and second circumferentialsides, and the first circumferential side includes a first weightreduction pocket.
 3. The non-contact seal assembly of claim 1, whereeach of the plurality of first and second seal shoes includes opposingfirst and second circumferential sides, and the first circumferentialside includes a first weight reduction pocket and the secondcircumferential side includes a second weight reduction pocket.
 4. Thenon-contact seal assembly of claim 2, where the first weight reductionpocket forms a through hole in the first circumferential side.
 5. Thenon-contact seal assembly of claim 1, where first weight reductionpocket forms a first through hole in the first circumferential side andthe second weight reduction pocket forms a second through hole in thesecond circumferential side.
 6. The non-contact seal assembly of claim2, where the plurality of seal shoes, the seal base and the plurality ofspring elements are formed from nickel alloy.
 7. The non-contact sealassembly of claim 2, where the plurality of seal shoes, the seal baseand the plurality of spring elements are formed from cobalt alloy. 8.The non-contact seal assembly of claim 1, where the first seal shoeextends circumferentially, at the first shoe end, between a first shoeside and a second shoe side for a seal shoe length.
 9. The non-contactseal assembly of claim 1, where the seal shoes collectively form asubstantially annular end surface at the second shoe end.
 10. Anon-contact seal assembly, comprising: a plurality of seal shoesarranged about a centerline in an annular array, the seal shoesincluding a first seal shoe extending axially along the centerlinebetween a first shoe end and a second shoe end; a seal basecircumscribing the annular array of the seal shoes; and a plurality ofspring elements, each of the spring elements radially between andconnecting a respective one of the seal shoes with the seal base, wherethe plurality of seal shoes each includes a weight reduction pocketformed in a circumferential region of a seal shoe stop that limitsradial travel of the seal shoe.
 11. The non-contact seal assembly ofclaim 10, where each of the plurality of first and second seal shoesincludes opposing first and second circumferential sides each uniquelyassociated with an associated one of a first or second shoe stop, andthe first circumferential side includes a first weight reduction pocket.12. The non-contact seal assembly of claim 10, where each of theplurality of first and second seal shoes includes opposing first andsecond circumferential sides, with the first circumferential sideincludes a first weight reduction pocket and the second circumferentialside includes a second weight reduction pocket.
 13. The non-contact sealassembly of claim 11, where the first weight reduction pocket forms athrough hole in the first circumferential side.
 14. The non-contact sealassembly of claim 10, where first weight reduction pocket forms a firstthrough hole in the first circumferential side and the second weightreduction pocket forms a second through hole in the secondcircumferential side.
 15. The non-contact seal assembly of claim 11,where the plurality of seal shoes, the seal base and the plurality ofspring elements are formed from nickel alloy.
 16. The non-contact sealassembly of claim 11, where the plurality of seal shoes, the seal baseand the plurality of spring elements are formed from cobalt alloy. 17.The non-contact seal assembly of claim 15, where the first seal shoeextends circumferentially, at the first shoe end, between a first shoeside and a second shoe side for a seal shoe length.
 18. The non-contactseal assembly of claim 16, where the seal shoes collectively form asubstantially annular end surface at the second shoe end.
 19. Anassembly for rotational equipment with an axial centerline, the assemblycomprising: a stator structure; a rotor structure; and a seal assemblythat substantially seals an annular gap between the stator structure andthe rotor structure, the seal assembly comprising a hydrostaticnon-contact seal device including a plurality of seal shoes, a seal baseand a plurality of spring elements; the seal shoes arranged about acenterline in an annular array, the seal shoes sealingly engaging therotor structure and including a first seal shoe extending axially alongthe centerline between a first shoe end and a second shoe end; the sealbase circumscribing the annular array of the seal shoes, the seal basemounted with the stator structure; and where the plurality of seal shoeseach includes a weight reduction pocket formed in a circumferentialregion of the seal shoe.
 20. The assembly of claim 19, where each of theplurality of first and second seal shoes includes opposing first andsecond circumferential sides, and the first circumferential sideincludes a first weight reduction pocket and the second circumferentialside includes a second weight reduction pocket.